65166 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

Accomplishment Instructions, paragraphs 

2.A through 2.C, of Erickson Service Bulletin 

No. 64B10–3, Revision D, dated October 15, 

2007, except you are not required to contact 

Erickson nor send hinge pins to them. A nondestructive testing (NDT) UT Level I Special, 

Level II, or Level III inspector who is 

qualified under the guidelines established by 

ASNT SNT–TC–1A, ISO 9712, or an FAAaccepted equivalent qualification standard 

for NDT inspection and evaluation, must 

perform the UT inspection. 

(5) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, 

perform a fluorescent-magnetic particle 

inspection (MPI) of each second stage 

planetary plate assembly, P/N 6435–20231– 

016, for a crack. 

(6) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 650 hours 

TIS, perform an MPI of each M/R shaft, P/ 

N 6435–20078–104, for a crack, paying 

particular attention to the lower spline area. 

(7) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 1,450 

hours TIS, perform an MPI of each M/R shaft, 

P/N 6435–20078–105, for a crack, paying 

particular attention to the lower spline area. 

(8) Within 150 hours TIS or before reaching 

3,375 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 3,375 

hours TIS, perform a fluorescent penetrant 

inspection of each housing lug on each servo 

housing, P/N S1565–20252–2, for a crack. 

(9) At each overhaul of the main gearbox 

assembly, P/N 6435–20400–053, –054, –058, 

–060, –062, –063, –064, –065, or –066, 

perform an MPI of the entire shaft of each 

M/R shaft assembly, P/N 6435–20078–014, 

–015, or –016, for a crack, paying particular 

attention to the rotating swashplate spherical 

bearing ball travel area, which is located 

approximately ten inches above the upper 

roller bearing journal shoulder. 

(10) If there is a crack in any part, before 

further flight, replace the cracked part. 

(11) At each overhaul of the damper 

assembly, P/N 6410–26200–042, replace the 

following parts with airworthy parts that 

have zero (0) hours TIS: 

(i) All Air Force-Navy Aeronautical 

Standard (AN), Aerospace Standard (AS), 

Military Standard (MS), and National 

Aerospace Standard (NAS) nuts, bolts, 

washers, and packings, except packing, P/N 

MS28775–011, installed on stud, P/N 

SHF111–11SN–12A; 

(ii) Lock washer, P/N SS5073–2; 

(iii) Nut, P/N SS5081–05; 

(iv) Felt seal, P/N S1510–26017; 

(v) Retaining ring, P/N UR106L; and 

(vi) Nut, P/N 6410–26214–101. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aerospace Engineer, Rotorcraft Certification 

Office, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5170; email 7-avs-asw170@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

Erickson Service Bulletin No. 64B General– 

1, Revision 19, dated September 15, 2010, 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For service information 

identified in this AD, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson, 

Director of Regulatory Compliance, 3100 

Willow Springs Rd., P.O. Box 3247, Central 

Point, OR 97502, telephone (541) 664–5544, 

fax (541) 664–2312, email address cerickson@

ericksonaircrane.com. You may review a 

copy of this information at the FAA, Office 

of the Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200: Main Rotor System; 6300: Main 

Rotor Drive System; 6410: Tail Rotor Blades; 

6500: Tail Rotor Drive System. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Erickson Service Bulletin No. 64B10–3, 

Revision D, dated October 15, 2007. 

(ii) Reserved. 

(3) For Erickson service information 

identified in this AD, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson, 

Director of Regulatory Compliance, 3100 

Willow Springs Rd, P.O. Box 3247, Central 

Point, OR 97502, telephone (541) 664–5544, 

fax (541) 664–2312, email address cerickson@

ericksonaircrane.com. 

(4) You may view this service information 

that is incorporated by reference at FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(5) You may also view this service 

information that is incorporated by reference 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on September 

25, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24955 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0625; Directorate 

Identifier 2013–NM–013–AD; Amendment 

39–17638; AD 2013–22–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 94–13–06 

for certain The Boeing Company Model 

747 series airplanes. AD 94–13–06 

required repetitive detailed inspections 

to detect cracking in certain fuselage 

upper deck tension ties, repair or 

modification of any cracked tension ties, 

and repetitive inspections of repaired 

and modified tension ties and repair or 

modification if necessary. AD 94–13–06 

also provided for optional terminating 

action for the repetitive detailed 

inspections of tension ties that had not 

been repaired or modified. This new AD 

retains the repetitive inspections, 

mandates the previously optional 

terminating modification, and adds, for 

tension ties that have not been repaired 

or modified, repetitive inspections that 

must be done concurrently with the 

existing repetitive inspections. This AD 

was prompted by an evaluation by the 

design approval holder indicating that 

the upper deck tension ties of the 

fuselage are subject to widespread 

fatigue damage. We are issuing this AD 

to prevent widespread fatigue damage of 

certain fuselage upper deck tension ties, 

which could result in reduced structural 

integrity of the airplane. 

DATES: This AD is effective December 5, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 5, 2013. 

ADDRESSES: For service information 

identified in this AD, contact, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P.O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Ave. 

SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65167 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6428; fax: (425) 917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 94–13–06, 

Amendment 39–8946 (59 FR 32879, 

June 27, 1994). AD 94–13–06 applied to 

the specified products. The NPRM 

published in the Federal Register on 

July 22, 2013 (78 FR 43839). The NPRM 

proposed to continue to require 

repetitive detailed inspections to detect 

cracking in certain fuselage upper deck 

tension ties, repair or modification of 

any cracked tension ties, and repetitive 

inspections of repaired and modified 

tension ties and repair or modification 

if necessary. The NPRM also proposed 

to mandate the previously optional 

terminating modification, and add, for 

tension ties that have not been repaired 

or modified, repetitive inspections that 

must be done concurrently with the 

existing repetitive inspections. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Boeing supported the NPRM (78 FR 

43839, July 22, 2013). 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 113 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Detailed inspections [retained action from AD 

94–13–06, Amendment 39–8946 (59 FR 

32879, June 27, 1994)].

5 work-hours × $85 per 

hour = $425.

$0 $425 per inspection 

cycle.

$48,025 per inspection 

cycle. 

Post-mod/repair inspections [new proposed action].1 work-hour × $85 per 

hour = $85.

0 $85 ............................... $9,605. 

Modification [new proposed action] ..................... Up to 112 work-hours × 

$85 per hour = up to 

$9,520.

0 Up to $9,520 ................ Up to $1,075,760. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

94–13–06, Amendment 39–8946 (59 FR 

32879, June 27, 1994), and adding the 

following new AD: 

2013–22–06 The Boeing Company: 

Amendment 39–17638; Docket No. 

FAA–2013–0625; Directorate Identifier 

2013–NM–013–AD. 

(a) Effective Date 

This AD is effective December 5, 2013. 

(b) Affected ADs 

This AD supersedes AD 94–13–06, 

Amendment 39–8946 (59 FR 32879, June 27, 

1994). 


wreier-aviles on DSK5TPTVN1PROD with RULES
65168 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–200B, and 747–200F 

series airplanes, certificated in any category, 

as listed in Boeing Alert Service Bulletin 

747–53A2371, Revision 2, dated December 

11, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

the upper deck tension ties of the fuselage are 

subject to widespread fatigue damage. We are 

issuing this AD to prevent widespread fatigue 

damage of certain fuselage upper deck 

tension ties, which could result in reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Repair/Modification 

Except as required by paragraph (k)(3) of 

this AD, at the applicable time specified in 

Tables 1 and 3 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Alert Service 

Bulletin 747–53A2371, Revision 2, dated 

December 11, 2012: Do detailed and surface 

high frequency eddy current (HFEC) 

inspections for cracks in the tension ties, as 

applicable, and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2371, Revision 2, 

dated December 11, 2012, except as required 

by paragraph (k)(2) of this AD. The effective 

date of AD 94–13–06, Amendment 39–8946 

(59 FR 32879, June 27, 1994) is July 27, 1994. 

Do all applicable corrective actions before 

further flight. Repeat the detailed and HFEC 

inspections thereafter at the time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2371, 

Revision 2, dated December 11, 2012, except 

as specified in paragraph (k)(1) of this AD. 

Repair of a tension tie, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2371, 

Revision 2, dated December 11, 2012, except 

as required by paragraph (k)(2) of this AD, 

terminates the requirements of this paragraph 

for that tension tie only. 

(h) Modification 

Except as provided by paragraph (k)(3) of 

this AD, at the applicable time specified in 

Table 3 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2371, 

Revision 2, dated December 11, 2012: Modify 

the tension ties, including doing an openhole HFEC inspection for cracks before 

enlarging the hole, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2371, Revision 2, 

dated December 11, 2012. Modification of the 

tension ties terminates the requirements of 

paragraph (g) of this AD. If any cracking is 

found, before further flight, do the repair 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(i) Post-Repair/Modification Inspections 

At the applicable time specified in Table 

2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2371, 

Revision 2, dated December 11, 2012: Do a 

detailed inspection of all repaired and 

modified tension ties, and do all applicable 

corrective actions, except as required by 

paragraph (k)(2) of this AD, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2371, 

Revision 2, dated December 11, 2012, except 

as required by paragraph (k)(2) of this AD. 

Repeat the inspection thereafter at the times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2371, 

Revision 2, dated December 11, 2012. Do all 

applicable corrective actions before further 

flight. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

modification required by paragraphs (g) and 

(h) of this AD if that modification was done 

before the effective date of this AD using 

Boeing Service Bulletin 747–53–2371, dated 

July 29, 1993; or Boeing Service Bulletin 

747–53–2371, Revision 1, dated April 27, 

1995; which are not incorporated by 

reference in this AD. Boeing Service Bulletin 

747–53–2371, dated July 29, 1993, was 

incorporated by reference in AD 94–13–06, 

Amendment 39–8946 (59 FR 32879, June 27, 

1994). 

(k) Exception to Service Information 

(1) Where Row 2 of Table 3 of paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2371, Revision 2, dated 

December 11, 2012, specifies repeating a 

‘‘detailed’’ inspection, ‘‘as given in Part 4’’ of 

this service information, the repetitive 

inspections required by this AD are ‘‘HFEC’’ 

inspections, done in accordance with Part 4 

and Figure 8 of Boeing Alert Service Bulletin 

747–53A2371, Revision 2, dated December 

11, 2012. 

(2) Where Boeing Alert Service Bulletin 

747–53A2371, Revision 2, dated December 

11, 2012, specifies contacting Boeing for 

repair instructions, or does not include repair 

instructions for a crack found in an area other 

than the aft tension tie area: Before further 

flight, do the repair using a method approved 

in accordance with the procedures specified 

in paragraph (l) of this AD. 

(3) Where Boeing Alert Service Bulletin 

747–53A2371, Revision 2, dated December 

11, 2012, specifies a compliance time of 

‘‘after the Revision 2 date of this service 

bulletin,’’ this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), has the authority 

to approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes ODA that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 94–13–06, 

Amendment 39–8946 (59 FR 32879, June 27, 

1994), are approved as AMOCs for the 

corresponding actions required by 

paragraphs (g), (h), and (i) of this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6428; fax: 

(425) 917–6590; email: nathan.p.weigand@

faa.gov. 

(2) Service information in this AD that is 

not incorporated by reference may be 

obtained at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

53A2371, Revision 2, dated December 11, 

2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65169 

Issued in Renton, Washington, on October 

15, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25307 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0446; Directorate 

Identifier 2010–SW–007–AD; Amendment 

39–17629; AD 2013–21–05] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH 

(Eurocopter) Model EC135 P1, P2, P2+, 

T1, T2, and T2+ helicopters. This AD 

requires inspecting each linear 

transducer bearing (bearing) for freedom 

of movement and replacing the bearing 

if there is binding or rough turning or 

if there is chafing or damage on the 

lower side of the floor. Also, this AD 

requires modifying and re-identifying a 

certain rod. This AD was prompted by 

an incident involving limited control of 

a tail rotor because of the binding of a 

bearing. The actions of this AD are 

intended to detect and replace each 

bearing subject to binding, which could 

lead to subsequent loss of control of the 

helicopter. 

DATES: This AD is effective December 5, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of December 5, 2013. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052, 

telephone (972) 641–0000 or (800) 232– 

0323, fax (972) 641–3775, or at http://

www.eurocopter.com/techpub. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the foreign 

authority’s AD, any incorporated-byreference service information, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (phone: 800–647–5527) is U.S. 

Department of Transportation, Docket 

Operations Office, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Matt 

Fuller, Senior Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email matthew.fuller@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 23, 2013, at 78 FR 30793, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Model EC135 P1, P2, P2+, T1, T2, and 

T2+ helicopters, with bearing, part 

number (P/N) LN9367GE6N2; rod, P/N 

L671M5040205; lever, P/N 

L671M5040101; and floor, P/N 

L533M1014101, L533M1014102, 

L533M1014103, L533M1014104, 

L533M1014105 or L533M1014106, 

installed. The NPRM proposed to 

require, at specified intervals, 

inspecting each bearing for freedom of 

movement. The NPRM also proposed, 

before further flight, if there is binding 

or rough turning, replacing the bearing 

or if there is chafing or damage on the 

lower side of the floor, replacing the 

bearing and repairing the floor, and, 

thereafter, installing a Teflon strip. The 

NPRM also proposed modifying the rod 

and re-identifying the rod and lever 

with a new part number. The 

requirements were intended to detect 

and replace each bearing subject to 

binding, which could lead to 

subsequent loss of control of the 

helicopter. 

The NPRM was prompted by AD No. 

2006–0318 R1, dated October 27, 2006, 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for all Eurocopter Model EC 

135 helicopters. EASA advises of an 

incident in which impaired control of 

an EC 135 tail rotor was detected. EASA 

states that according to examinations, 

the bearing of the linear transducer was 

subject to binding, which limited the 

control range. 

FAA’s Determination 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 30793, May 23, 2013). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are issuing this AD because we 

evaluated all information provided by 

EASA and determined the unsafe 

condition exists and is likely to exist or 

develop on other helicopters of these 

same type designs and that air safety 

and the public interest require adopting 

the AD requirements as proposed. 

Differences Between This AD and the 

EASA AD 

This AD does not refer to the 

compliance date of October 31, 2006, 

because that date has passed; instead we 

require compliance within 100 hours 

time-service (TIS). This AD does not 

require contacting Eurocopter customer 

support. This AD requires modifying 

each rod within 100 hours TIS, rather 

than within 800 hours TIS as specified 

in the EASA AD. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin EC135–67A–012, Revision 1, 

dated October 18, 2006 (ASB), which 

specifies inspecting the bearing of the 

linear transducer for freedom of 

movement and the lower side of the 

floor for chafing or damage. If there is 

binding, the ASB specifies replacing the 

bearing. If there is chafing or damage on 

the floor, the ASB specifies replacing 

the bearing and repairing the floor. The 

ASB also specifies modifying and 

reidentifying a certain rod. EASA 

classified this ASB as mandatory and 

issued EASA AD 2006–0318 R1, dated 

October 27, 2006, to ensure the 

continued airworthiness of these 

helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

214 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD: It will take about 10 workhours to inspect the bearing for freedom 

of movement at an average labor rate of 


wreier-aviles on DSK5TPTVN1PROD with RULES